US2652685A

US2652685A - Starting device for compressorturbine units

Info

Publication number: US2652685A
Application number: US26873A
Authority: US
Inventors: Andrew V D Willgoos
Original assignee: UNITED ARICRAFT CORP
Current assignee: UNITED ARICRAFT Corp
Priority date: 1948-05-13
Filing date: 1948-05-13
Publication date: 1953-09-22
Anticipated expiration: 1970-09-22

Description

Sept. 22, 1953 A. v. D. WILLGOOS Filed May 13, 1948 STARTING DEVICE FOR COMPRESSOR-TURBINE UNITS 3 Sheets-Sheet 1 flizoriieg Sept. 22, 1953 A. v. D. WILLGOOS 2,652,635

STARTING DEVICE FOR COMPRESSOR-TURBINE UNITS Filed May 13, 1948 3 Sheets-Sheet 2 I we 20 7' flair em TC. 5223005 .9

p 1953 A. v. D. WILLGOOS 2,652,685

STARTING DEVICE FOR COMPRESSOR-TURBINE UNITS Filed May 13, 1948 3 Sheets-Sheet 3 NIJNUIMF U! i lllllm A In we w 207 flzad're 20 K0. afiZQqoos Patented Sept. 22, 1953 TURBINE UNITS s'rmmc nnvrcs son comrns ssoa- I Andrew V. D. Wiiigoos, West Hartford, Conn., as-

.signor to United Aircraft Corporation, East Hartford. Conn., a corporation of Delaware Application May 13, i248,- Serial No. 26,873

. 1 This invention relates to a starting device for compressor-turbine units and particularly to an arrangement for using the exhaust gas from the starting device.

Most compressors, particularly of the axial flow type, have stationary turning vanes located at the air inlet ahead of the rotor to give an initial spin to, or otherwise direct, the entering air. Under certain conditions, especially during flight, if the power plant is used in aircraft, ice may accumulate on the vanes seriouslyreducing the area of the air inlet. A feature of this invention is the heating of the vanes by exhaust gas from the internal combustion starting engine. Another feature is the discharge of the exhaust gas from these vanes into the inlet air for the purpose of warming any of the compressor blades for the removal ofice thereon. One feature is the discharge of the exhaust gas from the vanes in such a direction as to engage with and cause turning of the blades of the compressor rotor.

When a compressor-turbine power plant is shut down, it is advantageous to continue spinning the rotors for a short time to prevent uneven cooling which might cause warping or damage to the compressor, turbine, shaft bearings, or other parts through the transfer of heat from the turbine rotor. A feature of the invention is the use of a starting engine for continuing the spinning of the power plant after the fuel is shut off.- This continued rotation will provide sufficient ventilation for cooling the power plant.

- During this cooling, exhaust gas from the engine may be delivered to the air stream through the power plant to prevent cooling too rapidly.

A feature of the invention is the interconnection of the starting engine and the compressorturbine unit by a hydraulic coupling that will become inoperative as soon as the compressor rotor overruns the starting engine. Another feature is the arrangement of the hydraulic coupling so that it may be filled for the purpose of cranking the starting engine from the turbine.

In some installations it may be advantageous to operate the power plant accessories without operation of the power plant itself. A feature of the invention is an arrangement for driving the accessories from the starting engine or from the compressor rotor selectively.

Other objects and advantages will be apparent from the specification and claims, and'from the accompanying drawings which illustrate an embodiment of the invention.

Fig. 1 is a sectional view through the power plant.

I Claims. (Cl. Gil-11) Fig. 2 isa sectional view similar to Fig. 1 substantially on line 22 of Fig. 3 showing the connection between thestarting engine and-the power plant on a larger scale.

,Fl Fig. 3 is a sectionalview along line 3-10! Fig. 4 is a fragmentary sectional view substantially along line 4-4 of Fig. 1. I

Fig. 5 is a view of a part of the control valve for one of the fluid couplings.

Fig. 6 is a fragmentary sectional view on line 6-6 of Fig. 5.

Fig. 7 isan elevation view of the power plant. With reference first to Figs. 1 and '7, the

power plant is shown only fragmentarily and includes a compressor 2 delivering air to one or more combustion chambers 4 in which the air is heated before it reaches the turbine 5. The compressor shown is of the axial flow type having a number of rows of stationaryvanes 6 supported by a casing 8 and alternating with rows of blades ID on the rotor I2. The'latter is connected as by a shaft [4 to the turbine rotor by which the compressor is driven. The compressor has an annular inlet Hi, the outer wall of which is formed by an extension; l8 of the casing and the inner wall of which is formed by a dome 20 within which are located the starting engine 22 together with the accessories 24' and the mechanism by which the accessories are driven as will hereinafter appear. The accessories and the starting motor are preferably carried by a supporting member 26 positioned within the casing 8 by a row of compressor inlet vanes 28, the latter being hollow as shown more clearly in Fig. 4. The vanes 28 may be arranged in the form of airfoils for imparting a tangential motion to the air in the direction of rotation of the rotor [2.

The starting engine is shown as a radial diesel,

although the specific engine construction is not important. It has been found that, with a radial engine, it is possible to locate the accessory drives between the adjacent cylinders 29 of the engine. The pistons 30 for the engine are connected to a crankshaft 32. A starting motor 34 is mounted at one end of the crankshaft for starting the engine 22. An overrunning clutch 36 permits the starting motor 34 to be stopped after it has cranked the engine.

The crankshaft 32 is also connected through a fluid coupling 38 to the forwardly'extending shaft 40 on which the compressor rotor is mounted. The fluid coupling, as better shown in Fig. 2, may be conventional, the impeller and runner of the coupling being connected respectively to the crankshaft and to the shaft 40. The flow of fluid into the coupling may be controlled by an annular ring valve 42, which, in the normal posi tion, admits fluid from a passage 44 in the crankshaft to the coupling. The ring valve 42 during the starting of the power plant is held in such a position that the ports 46 in the valve are in alignment with the ports 48 in the crankshaft. The valve is held in this position by a projecting pin 50 mounted'in the crankshaft and engaging in a slot 52 in the ring. when the power plant begins to operate under its own power and overspeeds the starting engine, the frictional drag on the ring 42 moves it angularly with respect to the crankshaft as limited by the pin 50 so that the

ports

46 and 48 are out of alignment, as shown in Fig. 5, and the admission of fluid to the coupling is discontinued. Small bleeds, not shown, in the coupling housing provide for the circulation of fluid through the coupling to prevent overheating and permit any fluid remaining in the coupling after the supply is shut oil to be drained. In addition to the automatic shut ofi of the fluid supply to the fluid coupling, the conduit 54 through which the fluid is supplied may be provided with a manually controlled valve 56. By closing this valve no fluid reaches the fluid coupling and the starting engine may operate independently of the main power plant.

The accessories 24, Fig. 2, may be driven selectively by the starting engine or by the power plant. One arrangement by which the drive from the starting engine may be accomplished includes a gear 58 keyed to the crankshaft and meshing with cooperating

gears

60 and 62 on the accessory drive shafts S4 and 66. An overrunning clutch 68 may be provided in the hub of the gear 80 (and 62) for driving the accessory shaft when

gear

60 or 62 is rotated in the accessory driving direction. The clutch 88 will permit the accessory drive shaft to rotate within gear 80 or 62 in the same direction.

The drive from the power plant is similar and includes a central gear connected to the main shaft through the medium of the housing 12 on the fluid coupling. The housing 12, as shown, may have a spline connection 14 with the hub of gear 10. This gear 10 meshes with gears 18 and 18 mounted on and connected as by overrunning clutches I9 to the same

accessory drive shafts

64 and 66. Thus the accessory drive shafts may be rotated by the gears 16 and 18 while the gears and 62 are stationary or the accessories may be driven through the

ears

68 and 62 while the gears 16 and 18 are stationary.

For relieving the load on the starting engine while it is being started, or while it is starting the main power plant, certain accessories may be disconnected from the drive as by hydraulic couplings located in the accessory drive connections. For example, as shown in Fig. 2, shaft 64 may be coupled to its accessory by a hydraulic coupling 88 to which fluid may be supplied throughthe hollow shaft 64. A suitable valve 8| in the supply line provides for controlling the supply of fluid.

It will be understood that it may be advantageous to drive the power plant accessories at a time when the power plant is not operating. The above described accessory drive makes possible operation of the accessories directly from the s'tartingfengine while the latter is disconnected from the power plant.

It may be necessary prior to starting of the power plant, or during operation, to prevent the formation of ice in the compressor or to remove an accumulation of ice already formed. This may be accomplished by delivering exhaust gas from the starting engine into the air stream entering the compressor. To this end, the exhaust ports of the engine cylinders are connected as by ducts 82, Fig. 1, to a chamber 84 in the housing 26. This chamber communicates, as shown, with the hollow vanes 28 which are open at their trailing edges, as shown in Fig. 4, for the discharge of the exhaust gas into the air stream as it enters the compressor. The formation of ice on the guide vanes is accordingly.

prevented and the air passing through the compressor is warmed suiflciently to prevent any ice formation in any part of the compressor. It may be understood that the delivery of the exhaust gas to the air stream may occur prior to starting of the power plant where ice has already formed within the compressor since the starting engine may operate independently of the main power plant. The hot gas may also be delivered to the compressor during operation 'of the main power plant. During the cooling When the power plant is in operation and heating of the air entering the compressor would not be advantageous, the exhaust gas may be discharged directly through the inlet vanes 28 to the atmosphere through ports in an annular ring 88 which surrounds the compressor casing externally of the vanes 28 and may be moved annularly to place the ports 88 in the ring in alignment with similar ports 90 in the casing which communicate with the hollow interiors of the inlet vanes. To assure flow through ports 88 and 90, the width of the opening in the trailing edge of vanes 28, as can be seen in Fig. 4, is relatively narrow so that the pressure drop across the opening is substantial.

It may be advantageous to provide for motoring the power plant, as, for example, when the power plant is being shut down. It has been found, if the power plant is turned over slowly during its cooling period, that the rate of cooling for all the parts is more uniform and damage to the power plant by reason of differential cooling is'less probable. With the arrangement above described, the starting engine may be used to turn the rotor of the power plant slowly during such cooling down period. During this cooling down period, any desirable part of the exhaust gas may be discharged into the air flowing through the power plant for controllingthe rate of cooling.

It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spiritas defined by the following claims.

Iclaim:

'1. In a power plant, a compressor, a turbine connected to and driving the compressor, a combustion chamber between the compressor and the turbine, and an internal combustion engine mechanically connected to the compressor and turbine for starting the power plant, in combination with means for discharging exhaust gas from the engine into the compressor inlet.

2. In a power plant, a compressor including a bladed rotor and having a series of stationary hollow vanes at its inlet end arranged for imparting a, tangential motion to the inlet air, a reciprocating engine for driving the compressor rotor, means for discharging exhaust gas from the engine through said hollow vanes, each of said vanes having an opening defined by and extending along the trailing edge thereof and through which exhaust gas is discharged from within said vanes into the airstream entering the compressor, said trailing edge openings directing said exhaust gas against said bladed rotor to cause turning of the rotor.

3. In a power plant, a compressor, a turbine connected to and driving the compressor, a, combustion chamber between the compressor and the turbine, and an internal combustion engine connected to the compressor and turbine for starting, in combination with means for discharging exhaust gas from the engine into the compressor inlet and a releasable driving means between the engine and the compressor and turbine, such that the engine may operate independently of the compressor and turbine.

4. A gas turbine power plant including a compressor having an air inlet, means for heating the compressed air from the compressor, and a turbine driven by the heated air, said turbine and compressor rotors being interconnected such that the turbine drives the compressor, in combination with an internal combustion engine, and means for discharging exhaust gas from the engine into the compressor inlet.

5. A gas turbine power plant including a compressor having an air inlet, means for heating the compressed air from the compressor and a turbine driven by the heated air, said turbine and compressor rotors being interconnected such that the turbine drives the compressor, in combination with an internal combustion engine for starting the power plant, a releasable connection between the engine and the compressor and turbine, means for releasing the connection when the compressor and turbine overrun the engine, and means for 6 discharging exhaust gas from the engine into the air in the compressor.

6. In a gas turbine power plant including a. compressor and turbine, each having a rotor, and a burner in which air from the compressor is heated before it reaches the turbine, the steps which involve spinning the rotors from an internal combustion engine after shut down of the power plant and simultaneously admitting exhaust gas from the engine to the compressor inlet.

7. A gas turbine power plant including a compressor having an air inlet, a compressor rotor, means for heating the compressed air from the compressor, and a turbine rotor driven by the heated air, said turbine and compressor rotors being interconnected such that the turbine rotor drives the compressor rotor, and accessories driven by said turbine rotor, in combination with an internal combustion engine, an hydraulic coupling connecting said engine and said power plant, said coupling comprising essentially an impeller and a rotor surrounded by a housing and means for driving said accessories selectively by said power plant through said coupling housing or by said engine.

ANDREW V. D. WILLGOOS.

References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 46,725 Strange Mar. 7, 1865 864,399 Wing Aug. 27, 1907 937,653 Sickenberger Oct. 19, 1909 943,420 Kershner Dec. 14, 1909 999,976 De Ferranti Aug. 8, 1911 1,495,567 Baentsch May 27,1924 1,953,486 Kiep Apr. 3, 1934 2,080,633 Ray May 18, 1937 2,129,534 Newell Sept. 6, 1938 2,195,139 Waseige Mar. 26, 1940 2,361,887 Traupel Oct. 31, 1944 2,432,359 Streid Dec. 9, 1947 2,441,135 Chalupa, May 11, 1948 2,474,068 Sammons et a1. June 21, 1949 2,557,933 Beaman et a1 June 26, 1951 2,634,049 Hodges et a1. Apr. 7, 1953 FOREIGN PATENTS Number Country Date 12,735 Great Britain May 31, 1906 700,192 France Dec. 22, 1930